Gas turbine engine turbine blade airfoil profile

ABSTRACT

A turbine blade for a gas turbine engine includes an airfoil that includes leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface that extends from a platform in a radial direction to a tip. The external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil described by a set of Cartesian coordinates set forth in Table 1. The Cartesian coordinates are provided by an axial coordinate scaled by a local axial chord. A circumferential coordinate is scaled by a local axial chord, and a span location, wherein the local axial chord corresponds to a width of the airfoil between the leading and trailing edges at the span location.

CROSS-REFERENCE TO RELATED APPLICATION

This application is related to co-pending application ______ by ______,application Ser. No. ______, filed ______.

BACKGROUND

This disclosure relates to a gas turbine engine, and more particularlyto an airfoil that may be incorporated into a gas turbine engine.

Gas turbine engines typically include a compressor section, a combustorsection and a turbine section. During operation, air is pressurized inthe compressor section and is mixed with fuel and burned in thecombustor section to generate hot combustion gases. The hot combustiongases are communicated through the turbine section, which extractsenergy from the hot combustion gases to power the compressor section andother gas turbine engine loads.

Both the compressor and turbine sections may include alternating seriesof rotating blades and stationary vanes that extend into the core flowpath of the gas turbine engine. For example, in the turbine section,turbine blades rotate and extract energy from the hot combustion gasesthat are communicated along the core flow path of the gas turbineengine. The turbine vanes, which generally do not rotate, guide theairflow and prepare it for the next set of blades.

In turbine blade design, there is an emphasis on stress-resistantairfoil and platform designs, with reduced losses, increased lift andturning efficiency, and improved turbine performance and service life.To achieve these results, non-linear flow analyses and complex strainmodeling are required, making practical results difficult to predict.Blade loading considerations also impose substantial design limitations,which cannot easily be generalized from one system to another.

SUMMARY

In one exemplary embodiment, a turbine blade for a gas turbine engineincludes an airfoil that includes leading and trailing edges joined byspaced apart pressure and suction sides to provide an exterior airfoilsurface that extends from a platform in a radial direction to a tip. Theexternal airfoil surface is formed in substantial conformance withmultiple cross-sectional profiles of the airfoil described by a set ofCartesian coordinates set forth in Table 1. The Cartesian coordinatesare provided by an axial coordinate scaled by a local axial chord. Acircumferential coordinate is scaled by a local axial chord, and a spanlocation, wherein the local axial chord corresponds to a width of theairfoil between the leading and trailing edges at the span location.

In a further embodiment of any of the above, the airfoil is a firststage turbine blade.

In a further embodiment of any of the above, the span locationcorresponds to a percentage of an overall span distance in the radialdirection from a point where the airfoil meets the platform toward thetip.

In a further embodiment of any of the above, the Cartesian coordinatesin Table 1 have a tolerance relative to the specified coordinates of±0.050 inches (±1.27 mm).

In another exemplary embodiment, a gas turbine engine includes acompressor section. A combustor is fluidly connected to the compressorsection. A turbine section is fluidly connected to the combustor. Theturbine section includes a high pressure turbine coupled to the highpressure compressor via a shaft. The turbine section includes a lowpressure turbine. The high pressure turbine includes an array of turbineblades. At least one turbine blade includes an airfoil having leadingand trailing edges joined by spaced apart pressure and suction sides toprovide an exterior airfoil surface extending from a platform in aradial direction to a tip. The external airfoil surface is formed insubstantial conformance with multiple cross-sectional profiles of theairfoil described by a set of Cartesian coordinates set forth inTable 1. The Cartesian coordinates are provided by an axial coordinatescaled by a local axial chord. A circumferential coordinate is scaled bya local axial chord, and a span location, wherein the local axial chordcorresponds to a width of the airfoil between the leading and trailingedges at the span location.

In a further embodiment of any of the above, the array is a first stagearray of turbine blades.

In a further embodiment of any of the above, the high pressure turbineincludes an array of fixed stator vanes upstream from the first stagearray of turbine blades.

In a further embodiment of any of the above, the first stage array ofturbine blades includes forty-four turbine blades.

In a further embodiment of any of the above, the span locationcorresponds to a percentage of an overall span distance in the radialdirection from a point where the airfoil meets the platform toward thetip.

In a further embodiment of any of the above, the Cartesian coordinatesin Table 1 have a tolerance relative to the specified coordinates of±0.050 inches (±1.27 mm).

In a further embodiment of any of the above, the high pressure turbineconsists of two arrays of turbine blades and two arrays of fixed statorvanes.

BRIEF DESCRIPTION OF THE DRAWINGS

The disclosure can be further understood by reference to the followingdetailed description when considered in connection with the accompanyingdrawings wherein:

FIG. 1 schematically illustrates a gas turbine engine embodiment.

FIG. 2 is a cross-sectional view through a high pressure turbinesection.

FIG. 3A is a perspective view of the airfoil having the disclosedcooling passage.

FIG. 3B is a plan view of the airfoil illustrating directionalreferences.

FIGS. 4A-4F illustrate different views of the airfoil from thedirections indicated in FIG. 3B.

FIG. 5 depict the span positions and local axial chords referenced inTable 1

DETAILED DESCRIPTION

FIG. 1 schematically illustrates an example gas turbine engine 20 thatincludes a fan section 22, a compressor section 24, a combustor section26 and a turbine section 28. Alternative engines might include anaugmenter section (not shown) among other systems or features. The fansection 22 drives air along a bypass flow path B while the compressorsection 24 draws air in along a core flow path C where air is compressedand communicated to a combustor section 26. In the combustor section 26,air is mixed with fuel and ignited to generate a high pressure exhaustgas stream that expands through the turbine section 28 where energy isextracted and utilized to drive the fan section 22 and the compressorsection 24.

Although the disclosed non-limiting embodiment depicts a turbofan gasturbine engine, it should be understood that the concepts describedherein are not limited to use with turbofans as the teachings may beapplied to other types of turbine engines; for example a turbine engineincluding a three-spool architecture in which three spoolsconcentrically rotate about a common axis and where a low spool enablesa low pressure turbine to drive a fan via a gearbox, an intermediatespool that enables an intermediate pressure turbine to drive a firstcompressor of the compressor section, and a high spool that enables ahigh pressure turbine to drive a high pressure compressor of thecompressor section.

The example engine 20 generally includes a low speed spool 30 and a highspeed spool 32 mounted for rotation about an engine central longitudinalaxis A relative to an engine static structure 36 via several bearingsystems 38. It should be understood that various bearing systems 38 atvarious locations may alternatively or additionally be provided.

The low speed spool 30 generally includes an inner shaft 40 thatconnects a fan 42 and a low pressure (or first) compressor section 44 toa low pressure (or first) turbine section 46. The inner shaft 40 drivesthe fan 42 through a speed change device, such as a geared architecture48, to drive the fan 42 at a lower speed than the low speed spool 30.The high-speed spool 32 includes an outer shaft 50 that interconnects ahigh pressure (or second) compressor section 52 and a high pressure (orsecond) turbine section 54. The inner shaft 40 and the outer shaft 50are concentric and rotate via the bearing systems 38 about the enginecentral longitudinal axis X.

A combustor 56 is arranged between the high pressure compressor 52 andthe high pressure turbine 54. In one example, the high pressure turbine54 includes at least two stages to provide a double stage high pressureturbine 54. In another example, the high pressure turbine 54 includesonly a single stage. As used herein, a “high pressure” compressor orturbine experiences a higher pressure than a corresponding “lowpressure” compressor or turbine.

The example low pressure turbine 46 has a pressure ratio that is greaterthan about 5. The pressure ratio of the example low pressure turbine 46is measured prior to an inlet of the low pressure turbine 46 as relatedto the pressure measured at the outlet of the low pressure turbine 46prior to an exhaust nozzle.

A mid-turbine frame 57 of the engine static structure 36 is arrangedgenerally between the high pressure turbine 54 and the low pressureturbine 46. The mid-turbine frame 57 further supports bearing systems 38in the turbine section 28 as well as setting airflow entering the lowpressure turbine 46.

The core airflow C is compressed by the low pressure compressor 44 thenby the high pressure compressor 52 mixed with fuel and ignited in thecombustor 56 to produce high speed exhaust gases that are then expandedthrough the high pressure turbine 54 and low pressure turbine 46. Themid-turbine frame 57 includes vanes 59, which are in the core airflowpath and function as an inlet guide vane for the low pressure turbine46. Utilizing the vane 59 of the mid-turbine frame 57 as the inlet guidevane for low pressure turbine 46 decreases the length of the lowpressure turbine 46 without increasing the axial length of themid-turbine frame 57. Reducing or eliminating the number of vanes in thelow pressure turbine 46 shortens the axial length of the turbine section28. Thus, the compactness of the gas turbine engine 20 is increased anda higher power density may be achieved.

The disclosed gas turbine engine 20 in one example is a high-bypassgeared aircraft engine. In a further example, the gas turbine engine 20includes a bypass ratio greater than about six (6), with an exampleembodiment being greater than about ten (10). The example gearedarchitecture 48 is an epicyclical gear train, such as a planetary gearsystem, star gear system or other known gear system, with a gearreduction ratio of greater than about 2.3.

In one disclosed embodiment, the gas turbine engine 20 includes a bypassratio greater than about ten (10:1) and the fan diameter issignificantly larger than an outer diameter of the low pressurecompressor 44. It should be understood, however, that the aboveparameters are only exemplary of one embodiment of a gas turbine engineincluding a geared architecture and that the present disclosure isapplicable to other gas turbine engines.

A significant amount of thrust is provided by the bypass flow B due tothe high bypass ratio. The fan section 22 of the engine 20 is designedfor a particular flight condition—typically cruise at about 0.8 Mach andabout 35,000 feet. The flight condition of 0.8 Mach and 35,000 ft., withthe engine at its best fuel consumption—also known as “bucket cruiseThrust Specific Fuel Consumption (‘TSFC’)”—is the industry standardparameter of pound-mass (lbm) of fuel per hour being burned divided bypound-force (lbf) of thrust the engine produces at that minimum point.

“Low fan pressure ratio” is the pressure ratio across the fan bladealone, without a Fan Exit Guide Vane (“FEGV”) system. The low fanpressure ratio as disclosed herein according to one non-limitingembodiment is less than about 1.50. In another non-limiting embodimentthe low fan pressure ratio is less than about 1.45.

“Low corrected fan tip speed” is the actual fan tip speed in ft/secdivided by an industry standard temperature correction of [(Tram °R)/518.7)^(0.5)]. The “Low corrected fan tip speed”, as disclosed hereinaccording to one non-limiting embodiment, is less than about 1150ft/second.

The example gas turbine engine includes the fan 42 that comprises in onenon-limiting embodiment less than about 26 fan blades. In anothernon-limiting embodiment, the fan section 22 includes less than about 20fan blades. Moreover, in one disclosed embodiment the low pressureturbine 46 includes no more than about 6 turbine rotors schematicallyindicated at 34. In another non-limiting example embodiment the lowpressure turbine 46 includes about 3 turbine rotors. A ratio between thenumber of fan blades 42 and the number of low pressure turbine rotors isbetween about 3.3 and about 8.6. The example low pressure turbine 46provides the driving power to rotate the fan section 22 and thereforethe relationship between the number of turbine rotors 34 in the lowpressure turbine 46 and the number of blades 42 in the fan section 22disclose an example gas turbine engine 20 with increased power transferefficiency.

Referring to FIG. 2, a cross-sectional view through a high pressureturbine section 54 is illustrated. In the example high pressure turbinesection 54, first and second arrays 54 b, 54 d of circumferentiallyspaced fixed vanes 60, 62 are axially spaced apart from one another. Afirst stage array 54 a of circumferentially spaced turbine blades 64 isarranged axially between the first and second fixed vane arrays 54 b, 54d. A second stage array 54 c of circumferentially spaced turbine blades66 is arranged aft of the second array 54 b of fixed vanes 62. The firstand second stage arrays 54 a, 54 c are arranged within a core flow pathC and are operatively connected to a spool 32.

A root 74 of each turbine blade 64 is mounted to the rotor disk 68. Theturbine blade 64 includes a platform 76, which provides the inner flowpath, supported by the root 74. An airfoil 78 extending in a radialdirection R from the platform 76 to a tip 80. It should be understoodthat the turbine blades may be integrally formed with the rotor suchthat the roots are eliminated. In such a configuration, the platform isprovided by the outer diameter of the rotor. The airfoil 78 providesleading and trailing edges 82, 84. The tip 80 is arranged adjacent to ablade outer air seal 70 mounted to a turbine case 72. A platform 58 ofthe second fixed vane array 62 is arranged in an overlappingrelationship with the turbine blades 64, 66.

Referring to FIGS. 3A and 3B, the airfoil 78 somewhat schematicallyillustrates exterior airfoil surface extending in a chord-wise directionC from a leading edge 82 to a trailing edge 84. The airfoil 78 isprovided between pressure (concave) and suction (convex) sides 86, 88 inan airfoil thickness direction T, which is generally perpendicular tothe chord-wise direction C. Multiple turbine blades 64 are arrangedcircumferentially in a circumferential direction A. The airfoil 78extends from the platform 76 in the radial direction R, or spanwise, tothe tip 80. The exterior airfoil surface may include multiple filmcooling holes (not shown).

The exterior surface of the airfoil 78 generates lift based upon itsgeometry and direct flow along the core flow path C. Various views ofthe airfoil 78 of the turbine blade 64 are shown in FIGS. 4A-4F. In oneexample, the first stage array 54 b consists of forty-four turbineblades 64, but the number may vary according to engine size. The turbineblades 64 are constructed from a high strength, heat resistant materialsuch as a nickel-based or cobalt-based superalloy, or of a hightemperature, stress resistant ceramic or composite material. In cooledconfigurations, internal fluid passages and external cooling aperturesprovide for a combination of impingement and film cooling. In addition,one or more thermal barrier coatings, abrasion-resistant coatings orother protective coatings may be applied to the turbine blade 64.

The geometries of airfoil 78 are described in terms of Cartesiancoordinates defined along x, y and z axes, which respectively correspondto the axial (x), circumferential (a) and radial (span) directions shownin FIGS. 3A and 3B. The span coordinate is provided as a percentagetaken from a point P where the airfoil meets the platform 76, asschematically illustrated in FIG. 5. The overall span is the distancefrom the point P to the tip 80 in the radial direction R. By way ofexample, the “25% span” is 25% the distance from the point P toward thetip 80 in the radial direction R. The axial (x) and circumferential (a)coordinates are normalized by the local axial chord for the give spanlocation. By way of example, local axial chord for axial (x) andcircumferential (a) coordinates associated with the 25% span correspondsto the width of the airfoil 78 between the leading and trailing edges82, 84 at the 25% span location.

The contour of the airfoil 78 is set forth in Table 1, which providesthe axial (x), circumferential (a) and span coordinates. The axial andcircumferential coordinates in Table 1 are in inches, but can beconverted to metric (mm) by multiplying by 25.4. Three dimensionalairfoil surfaces are formed by joining adjacent points in Table 1 in asmooth manner and joining adjacent sections or sectional profiles alongthe span. The manufacturing tolerance relative to the specifiedcoordinates is ±±0.050 inches (±1.27 mm). The coordinates define pointson a cold, uncoated, stationary airfoil surface, in a plane at 0% span.Additional elements such as cooling holes, protective coatings, filletsand seal structures may also be formed onto the specified airfoilsurface, or onto an adjacent platform surface, but these elements arenot necessarily described by the normalized coordinates.

TABLE 1 Normalized Section 1 Normalized Section 2 Normalized Section 3 xa % Span x a % Span x a % Span 0.017703 0.686308 0 0.009708 0.95771612.5 0.005433 1.17377 25 0.016441 0.68816 0 0.008662 0.960065 12.50.004546 1.176328 25 0.015337 0.689863 0 0.007962 0.961709 12.5 0.004011.178011 25 0.012994 0.693781 0 0.006493 0.96558 12.5 0.002938 1.18179625 0.011222 0.697077 0 0.005323 0.96899 12.5 0.002005 1.185764 250.008654 0.702516 0 0.00371 0.975119 12.5 0.000901 1.192086 25 0.0057420.710089 0 0.00215 0.983273 12.5 0.000101 1.200852 25 0.002856 0.7203870 0.001166 0.993442 12.5 0.000177 1.211351 25 0.000573 0.734812 00.001459 1.007621 12.5 0.001998 1.22591 25 0.000139 0.753426 0 0.0044671.02611 12.5 0.006984 1.244535 25 0.002937 0.777023 0 0.011067 1.04692712.5 0.01572 1.265257 25 0.009316 0.802749 0 0.021207 1.070454 12.50.02837 1.289168 25 0.018213 0.832857 0 0.034666 1.097867 12.5 0.0458541.316232 25 0.029419 0.866547 0 0.051294 1.127901 12.5 0.068615 1.34392125 0.043514 0.903681 0 0.073027 1.160658 12.5 0.098331 1.37077 250.061214 0.943889 0 0.101561 1.193621 12.5 0.135754 1.393604 25 0.0834360.986554 0 0.138792 1.22328 12.5 0.181944 1.409127 25 0.111389 1.0306610 0.18316 1.245388 12.5 0.234459 1.413505 25 0.145229 1.072965 0 0.230851.258075 12.5 0.288658 1.405815 25 0.187852 1.112632 0 0.282488 1.26198612.5 0.344197 1.386669 25 0.23925 1.144242 0 0.336417 1.25666 12.50.398392 1.357793 25 0.29664 1.162133 0 0.389729 1.242253 12.5 0.4483211.322492 25 0.359298 1.163449 0 0.443604 1.217694 12.5 0.496097 1.28075525 0.419826 1.148147 0 0.493858 1.184859 12.5 0.539644 1.235535 250.475733 1.11999 0 0.540478 1.144931 12.5 0.580135 1.186768 25 0.5257831.08317 0 0.582848 1.100086 12.5 0.617381 1.135477 25 0.571094 1.03985 00.621407 1.051635 12.5 0.651579 1.082239 25 0.612039 0.99183 0 0.6565821.000328 12.5 0.683048 1.027422 25 0.648433 0.941312 0 0.68844 0.94734612.5 0.712024 0.971467 25 0.681566 0.888308 0 0.717867 0.892388 12.50.739126 0.913899 25 0.711724 0.833858 0 0.744866 0.836498 12.5 0.7641910.855749 25 0.739901 0.7774 0 0.770063 0.779327 12.5 0.787602 0.79683 250.765898 0.720391 0 0.793527 0.721473 12.5 0.809576 0.737181 25 0.7902670.662615 0 0.815323 0.663655 12.5 0.829979 0.67778 25 0.813276 0.6042150 0.836054 0.604791 12.5 0.849361 0.617559 25 0.835123 0.545342 00.855729 0.545414 12.5 0.867803 0.556651 25 0.855089 0.488677 0 0.8735880.488529 12.5 0.884538 0.498195 25 0.874419 0.43128 0 0.890837 0.43080212.5 0.900566 0.439252 25 0.892426 0.375633 0 0.906788 0.375016 12.50.915345 0.382249 25 0.908575 0.323998 0 0.920995 0.323401 12.5 0.9284940.329319 25 0.92373 0.274108 0 0.934426 0.272841 12.5 0.940892 0.27746925 0.937349 0.228129 0 0.94635 0.226616 12.5 0.951813 0.230191 250.949537 0.186095 0 0.956959 0.184426 12.5 0.961481 0.187067 25 0.9603770.148025 0 0.96636 0.146197 12.5 0.97002 0.14797 25 0.970024 0.113624 00.974652 0.111855 12.5 0.977491 0.112973 25 0.978376 0.083456 0 0.9818650.081479 12.5 0.984017 0.081801 25 0.985542 0.057291 0 0.988016 0.05522512.5 0.989546 0.054951 25 0.991427 0.035616 0 0.993123 0.033157 12.50.994167 0.032196 25 0.996378 0.017254 0 0.997356 0.014732 12.5 0.9979740.01323 25 0.999828 0.003119 0 0.999929 0.000489 12.5 0.999976 −0.0011725 0.998881 −0.0079 0 0.998182 −0.01013 12.5 0.997725 −0.01167 250.995557 −0.01527 0 0.994764 −0.01683 12.5 0.994053 −0.01829 25 0.99171−0.02008 0 0.990368 −0.02188 12.5 0.989307 −0.02346 25 0.988428 −0.022910 0.987144 −0.02446 12.5 0.985976 −0.02599 25 0.984955 −0.0251 00.983662 −0.02653 12.5 0.982411 −0.02801 25 0.983342 −0.0259 0 0.982174−0.02723 12.5 0.980979 −0.02865 25 0.981272 −0.02674 0 0.97996 −0.028112.5 0.978617 −0.02954 25 0.980181 −0.02712 0 0.979116 −0.02838 12.50.977697 −0.02982 25 0.978966 −0.02747 0 0.977263 −0.02888 12.5 0.975579−0.03037 25 0.976514 −0.02802 0 0.974483 −0.02941 12.5 0.972477 −0.0308925 0.974059 −0.02835 0 0.971795 −0.02968 12.5 0.969334 −0.03109 250.970332 −0.02843 0 0.96741 −0.02956 12.5 0.964595 −0.0308 25 0.965361−0.02778 0 0.961817 −0.02847 12.5 0.958355 −0.02925 25 0.95932 −0.0257 00.955285 −0.0256 12.5 0.951509 −0.02578 25 0.952406 −0.02106 0 0.948042−0.01961 12.5 0.943889 −0.01847 25 0.945828 −0.01219 0 0.94139 −0.0084812.5 0.937111 −0.00548 25 0.939835 0.00025 0 0.934594 0.005582 12.50.929636 0.010207 25 0.932577 0.014367 0 0.926401 0.02195 12.5 0.9207050.028656 25 0.923517 0.030854 0 0.916544 0.040916 12.5 0.910212 0.04995625 0.912836 0.049037 0 0.905074 0.062142 12.5 0.898138 0.073993 250.900359 0.06894 0 0.891877 0.085609 12.5 0.884426 0.100725 25 0.8858820.09062 0 0.876907 0.111158 12.5 0.869108 0.129939 25 0.869362 0.1138920 0.860012 0.138855 12.5 0.852002 0.161815 25 0.850529 0.138892 00.841019 0.168752 12.5 0.83304 0.196303 25 0.830531 0.163982 0 0.8208090.199369 12.5 0.812932 0.231983 25 0.808224 0.190504 0 0.798489 0.23186912.5 0.790853 0.270184 25 0.784388 0.217403 0 0.774699 0.265274 12.50.767536 0.309498 25 0.759911 0.243695 0 0.750343 0.298275 12.5 0.7437740.348552 25 0.733927 0.270317 0 0.724578 0.332002 12.5 0.718733 0.38867425 0.707095 0.296569 0 0.698031 0.365622 12.5 0.693036 0.428805 250.680071 0.32186 0 0.671334 0.398335 12.5 0.667184 0.468172 25 0.6524360.346632 0 0.64408 0.430701 12.5 0.640824 0.507316 25 0.624235 0.3708520 0.616253 0.462791 12.5 0.613967 0.546202 25 0.595246 0.394701 00.587908 0.494392 12.5 0.586619 0.584795 25 0.566297 0.417509 0 0.5592170.525505 12.5 0.558784 0.623061 25 0.53658 0.439911 0 0.529938 0.55623612.5 0.530466 0.660965 25 0.506213 0.461776 0 0.499939 0.586706 12.50.501377 0.698828 25 0.475944 0.482552 0 0.470314 0.615747 12.5 0.4727140.735081 25 0.444958 0.502772 0 0.439274 0.645332 12.5 0.442456 0.77220725 0.4134 0.52227 0 0.408001 0.673966 12.5 0.411986 0.808396 25 0.3807450.541262 0 0.375996 0.7021 12.5 0.380898 0.844053 25 0.348049 0.559029 00.343622 0.729464 12.5 0.349164 0.879096 25 0.31637 0.574998 0 0.311910.755192 12.5 0.317778 0.912351 25 0.283618 0.590138 0 0.279465 0.78024912.5 0.285643 0.944882 25 0.251478 0.603528 0 0.247576 0.803635 12.50.253819 0.975487 25 0.221138 0.614702 0 0.217428 0.824508 12.5 0.2234751.00306 25 0.191513 0.62407 0 0.188299 0.843323 12.5 0.19393 1.028262 250.163834 0.631249 0 0.160403 0.860157 12.5 0.165297 1.050977 25 0.1382770.636304 0 0.134385 0.874488 12.5 0.138369 1.070619 25 0.11493 0.6393520 0.110183 0.886356 12.5 0.112962 1.087418 25 0.09401 0.642086 00.088717 0.895722 12.5 0.090276 1.100789 25 0.075859 0.646508 0 0.0692580.90372 12.5 0.069426 1.111505 25 0.060588 0.652172 0 0.052253 0.91184312.5 0.050984 1.121242 25 0.04824 0.658491 0 0.039505 0.920626 12.50.036917 1.131132 25 0.039374 0.664321 0 0.030194 0.928757 12.5 0.0265871.140532 25 0.032602 0.669744 0 0.023311 0.936139 12.5 0.019182 1.14904325 0.02807 0.67398 0 0.018921 0.941801 12.5 0.014651 1.155394 25 0.024440.677813 0 0.015816 0.946313 12.5 0.011481 1.160615 25 0.021886 0.6807950 0.013535 0.95004 12.5 0.009148 1.165051 25 0.020663 0.682318 00.012261 0.952508 12.5 0.007883 1.167741 25 0.019265 0.684145 0 0.0108650.955331 12.5 0.00644 1.171133 25 0.018263 0.685518 0 0.01025 0.95646312.5 0.005993 1.172273 25 Normalized Section 4 Normalized Section 5 x a% Span x a % Span 0.003628 1.357935 37.5 0.002466 1.538709 50 0.0028731.360543 37.5 0.001904 1.541171 50 0.002362 1.362322 37.5 0.0015071.543159 50 0.001411 1.366024 37.5 0.000858 1.547099 50 0.0005241.370772 37.5 0.000273 1.552452 50 0.000308 1.377047 37.5 2.74E−061.55876 50 0.000664 1.386411 37.5 0.00043 1.568404 50 1.83E−05 1.39741837.5 0.002173 1.579746 50 0.002815 1.412573 37.5 0.00658 1.595156 500.008997 1.431318 37.5 0.014843 1.613641 50 0.019035 1.452981 37.50.027703 1.635012 50 0.033685 1.478077 37.5 0.046177 1.658201 500.055047 1.505214 37.5 0.072304 1.68071 50 0.084394 1.530223 37.50.107294 1.698058 50 0.122031 1.549127 37.5 0.150103 1.705405 500.166487 1.558827 37.5 0.197808 1.70038 50 0.216587 1.557988 37.50.247611 1.683451 50 0.269952 1.545712 37.5 0.297645 1.656328 500.323245 1.522743 37.5 0.346164 1.621368 50 0.376536 1.489594 37.50.394132 1.578926 50 0.427483 1.448415 37.5 0.440107 1.531033 500.473843 1.402726 37.5 0.482813 1.480104 50 0.517688 1.352209 37.50.523703 1.425218 50 0.557794 1.29967 37.5 0.561886 1.368111 50 0.595141.244984 37.5 0.59755 1.309153 50 0.629697 1.18884 37.5 0.6306651.249081 50 0.66179 1.13125 37.5 0.661703 1.187675 50 0.691511 1.07276337.5 0.690687 1.125466 50 0.719175 1.013401 37.5 0.717821 1.062583 500.745262 0.952651 37.5 0.743508 0.998557 50 0.769565 0.891498 37.50.767598 0.934199 50 0.792343 0.829841 37.5 0.790334 0.86931 50 0.8138380.767494 37.5 0.811845 0.803911 50 0.833995 0.705038 37.5 0.8322550.737959 50 0.852958 0.642558 37.5 0.851333 0.672623 50 0.8711090.579108 37.5 0.869673 0.606184 50 0.8877 0.517774 37.5 0.8865520.541666 50 0.903391 0.456693 37.5 0.902429 0.477811 50 0.9179030.397373 37.5 0.917161 0.415621 50 0.930891 0.341841 37.5 0.930380.357254 50 0.942969 0.288072 37.5 0.942535 0.301305 50 0.95361 0.23890137.5 0.953318 0.249739 50 0.963 0.194049 37.5 0.962806 0.202788 500.971274 0.153365 37.5 0.971148 0.160215 50 0.978483 0.116989 37.50.978411 0.12214 50 0.984793 0.084429 37.5 0.984774 0.087963 50 0.9901050.056473 37.5 0.990111 0.058703 50 0.994544 0.032735 37.5 0.9945610.033869 50 0.998222 0.01278 37.5 0.99826 0.012915 50 0.999974 −0.0018637.5 0.999926 −0.00226 50 0.997502 −0.01255 37.5 0.997297 −0.01334 500.993429 −0.01964 37.5 0.992824 −0.02098 50 0.988541 −0.02483 37.50.987933 −0.02611 50 0.984927 −0.02749 37.5 0.983923 −0.02904 500.981207 −0.02954 37.5 0.98002 −0.03115 50 0.979761 −0.03017 37.50.978532 −0.03179 50 0.977247 −0.03108 37.5 0.975864 −0.03274 500.975938 −0.03146 37.5 0.974102 −0.03323 50 0.973917 −0.03195 37.50.972246 −0.03365 50 0.970497 −0.03246 37.5 0.968503 −0.03416 500.966706 −0.0326 37.5 0.964168 −0.03423 50 0.961883 −0.03214 37.50.959145 −0.03363 50 0.954982 −0.03016 37.5 0.951659 −0.03125 500.947956 −0.02621 37.5 0.944239 −0.0267 50 0.939927 −0.01763 37.50.935913 −0.01689 50 0.932959 −0.0032 37.5 0.92863 −0.00124 50 0.9249160.014117 37.5 0.919988 0.017699 50 0.915417 0.034481 37.5 0.9098360.039914 50 0.904404 0.057973 37.5 0.898108 0.065538 50 0.8918550.084583 37.5 0.884795 0.094567 50 0.877754 0.114272 37.5 0.869886 0.12750 0.862127 0.146925 37.5 0.853372 0.162829 50 0.844854 0.182689 37.50.835237 0.202048 50 0.825953 0.221432 37.5 0.815464 0.24465 50 0.8060780.261675 37.5 0.794827 0.288921 50 0.784302 0.305223 37.5 0.7722680.337075 50 0.761658 0.349813 37.5 0.749108 0.386231 50 0.7387260.394252 37.5 0.725817 0.435345 50 0.714675 0.440062 37.5 0.701570.486104 50 0.690156 0.485875 37.5 0.677148 0.536804 50 0.6654330.531194 37.5 0.652533 0.587436 50 0.640265 0.576378 37.5 0.6276970.637988 50 0.614755 0.621151 37.5 0.602788 0.688099 50 0.5885910.666102 37.5 0.577254 0.738782 50 0.562029 0.710607 37.5 0.5515790.78897 50 0.535014 0.754803 37.5 0.525547 0.838974 50 0.507207 0.79916437.5 0.498835 0.889257 50 0.479672 0.841929 37.5 0.4722 0.938243 500.450807 0.88533 37.5 0.444709 0.987467 50 0.421481 0.928054 37.50.416553 1.036324 50 0.391438 0.970244 37.5 0.387612 1.08473 50 0.3605251.011827 37.5 0.357751 1.132569 50 0.329688 1.051325 37.5 0.3278721.178112 50 0.297817 1.089993 37.5 0.29678 1.222856 50 0.265884 1.12635237.5 0.265433 1.265087 50 0.235052 1.159103 37.5 0.234976 1.303256 500.204445 1.189241 37.5 0.204325 1.338783 50 0.174754 1.216062 37.50.174782 1.370309 50 0.146673 1.239238 37.5 0.146816 1.397763 500.119919 1.259334 37.5 0.120132 1.421884 50 0.095671 1.275783 37.50.095659 1.442319 50 0.073539 1.289165 37.5 0.073557 1.459469 50 0.0541.300415 37.5 0.054056 1.473635 50 0.038098 1.310965 37.5 0.0373151.485931 50 0.02642 1.321295 37.5 0.0249 1.49775 50 0.018276 1.33063837.5 0.016554 1.508121 50 0.013449 1.337416 37.5 0.01173 1.515678 500.009872 1.343446 37.5 0.008067 1.522746 50 0.007318 1.348614 37.50.005611 1.528582 50 0.006119 1.351223 37.5 0.00462 1.531334 50 0.0046291.35501 37.5 0.003334 1.535434 50 0.004211 1.356272 37.5 0.002951.536822 50 Normalized Section 6 Normalized Section 7 x a % Span x a %Span 0.000886 1.73725 62.5 0.001243 1.95021 75 0.000672 1.739326 62.50.001569 1.951955 75 0.000672 1.741663 62.5 0.002121 1.954511 750.000899 1.746413 62.5 0.003591 1.959972 75 0.001263 1.75181 62.50.00529 1.964946 75 0.002314 1.758435 62.5 0.008185 1.971728 75 0.0044521.767703 62.5 0.012706 1.980041 75 0.00849 1.77885 62.5 0.0198131.990172 75 0.016143 1.793587 62.5 0.031617 2.002907 75 0.02871 1.8108262.5 0.049291 2.016487 75 0.047618 1.828568 62.5 0.074429 2.026797 750.07322 1.843417 62.5 0.106486 2.029058 75 0.105332 1.852561 62.50.14277 2.021008 75 0.143482 1.853765 62.5 0.180987 2.003267 75 0.1862361.844837 62.5 0.219973 1.977265 75 0.23157 1.82499 62.5 0.2595641.943901 75 0.277476 1.795106 62.5 0.299675 1.903741 75 0.3229731.756883 62.5 0.340268 1.857094 75 0.366759 1.712987 62.5 0.3797971.806137 75 0.410267 1.662929 62.5 0.419739 1.749207 75 0.4522751.608744 62.5 0.45863 1.688476 75 0.491918 1.552243 62.5 0.4955681.625785 75 0.529862 1.493002 62.5 0.530694 1.561421 75 0.5658891.431462 62.5 0.564395 1.495095 75 0.599753 1.368417 62.5 0.5963761.427787 75 0.631424 1.304537 62.5 0.626652 1.359912 75 0.66122 1.23984662.5 0.655241 1.291898 75 0.689491 1.173945 62.5 0.682896 1.222239 750.716059 1.107733 62.5 0.709028 1.1527 75 0.741269 1.040776 62.50.733938 1.082815 75 0.765077 0.973544 62.5 0.757677 1.012715 750.787802 0.905455 62.5 0.780652 0.941379 75 0.80931 0.837211 62.50.80245 0.870273 75 0.829828 0.768403 62.5 0.823313 0.798853 75 0.8491520.699968 62.5 0.843279 0.727156 75 0.867706 0.630705 62.5 0.8624210.655083 75 0.884755 0.563734 62.5 0.879974 0.585862 75 0.9009660.496835 62.5 0.896953 0.515809 75 0.915987 0.431836 62.5 0.9126770.447952 75 0.929331 0.37149 62.5 0.92648 0.385807 75 0.941636 0.31347762.5 0.939333 0.325582 75 0.95267 0.259432 62.5 0.950938 0.269074 750.962321 0.210486 62.5 0.961033 0.218141 75 0.970793 0.166162 62.50.969887 0.172001 75 0.978169 0.126511 62.5 0.977572 0.130738 750.984635 0.090901 62.5 0.984267 0.093829 75 0.99005 0.060459 62.50.989882 0.062135 75 0.994568 0.034609 62.5 0.994553 0.035236 750.998281 0.013082 62.5 0.998308 0.013225 75 0.999854 −0.00309 62.50.999773 −0.00418 75 0.996888 −0.01464 62.5 0.99638 −0.01623 75 0.992166−0.02246 62.5 0.991467 −0.02406 75 0.987305 −0.02749 62.5 0.986511−0.02912 75 0.982879 −0.03072 62.5 0.98176 −0.03255 75 0.978812 −0.0328962.5 0.977531 −0.03479 75 0.977301 −0.03353 62.5 0.976001 −0.03544 750.97448 −0.03453 62.5 0.973019 −0.03649 75 0.972471 −0.03508 62.50.970891 −0.03708 75 0.970529 −0.0355 62.5 0.968694 −0.03755 75 0.966441−0.03602 62.5 0.964232 −0.03809 75 0.961954 −0.03607 62.5 0.959738−0.03811 75 0.956238 −0.03529 62.5 0.953086 −0.03715 75 0.94831 −0.0325862.5 0.944711 −0.03411 75 0.939962 −0.02702 62.5 0.935271 −0.02741 750.93156 −0.01605 62.5 0.926787 −0.01514 75 0.923785 0.000881 62.50.918371 0.0032 75 0.914362 0.021426 62.5 0.908023 0.025469 75 0.9032080.045569 62.5 0.895647 0.05172 75 0.890256 0.073379 62.5 0.8811750.081916 75 0.875482 0.104821 62.5 0.864534 0.116023 75 0.8588250.139937 62.5 0.845651 0.154002 75 0.840256 0.1787 62.5 0.8244570.195818 75 0.819862 0.220883 62.5 0.801096 0.241059 75 0.7973710.266964 62.5 0.775006 0.290724 75 0.77387 0.314762 62.5 0.7476280.342117 75 0.748317 0.366474 62.5 0.717976 0.397243 75 0.722043 0.4194962.5 0.68721 0.454207 75 0.695737 0.47257 62.5 0.656525 0.511162 750.668593 0.527528 62.5 0.625008 0.570201 75 0.641678 0.582376 62.50.59402 0.629176 75 0.614735 0.637714 62.5 0.563236 0.689062 75 0.5880940.692998 62.5 0.533249 0.749002 75 0.561795 0.748196 62.5 0.5040310.809275 75 0.535506 0.803923 62.5 0.475658 0.869833 75 0.5094580.859517 62.5 0.447944 0.930796 75 0.483394 0.915138 62.5 0.4207510.992058 75 0.457074 0.970996 62.5 0.393977 1.053503 75 0.4308031.026202 62.5 0.367519 1.115045 75 0.404169 1.081462 62.5 0.3412541.176682 75 0.37709 1.136519 62.5 0.315153 1.238222 75 0.34947 1.19133162.5 0.289049 1.2998 75 0.321209 1.245793 62.5 0.262862 1.361349 750.293163 1.298002 62.5 0.237369 1.420806 75 0.264206 1.349723 62.50.211602 1.480203 75 0.235239 1.399093 62.5 0.186363 1.537456 750.207334 1.444206 62.5 0.162526 1.590485 75 0.179389 1.486913 62.50.139161 1.641292 75 0.152736 1.525394 62.5 0.117211 1.6878 75 0.1276261.559604 62.5 0.096731 1.729988 75 0.103913 1.590047 62.5 0.0777951.767853 75 0.082109 1.616585 62.5 0.060488 1.801414 75 0.0624831.639426 62.5 0.044906 1.83071 75 0.044924 1.659043 62.5 0.0306681.856677 75 0.029712 1.675374 62.5 0.018591 1.878065 75 0.018091 1.6899162.5 0.009069 1.895951 75 0.010804 1.701872 62.5 0.003866 1.909996 750.00674 1.711002 62.5 0.001307 1.920941 75 0.003939 1.719405 62.50.000165 1.930634 75 0.002355 1.725717 62.5 1.07E−05 1.937251 750.001813 1.729217 62.5 0.000195 1.941646 75 0.001222 1.733551 62.50.000621 1.946065 75 0.001021 1.735005 62.5 0.000835 1.947668 75

In general, the turbine blade airfoil 78, as described herein, has acombination of axial sweep and tangential lean. Depending onconfiguration, the lean and sweep angles sometimes vary by up to ±10° ormore. In addition, the turbine blade 78 is sometimes rotated withrespect to a radial axis or a normal to the platform or shroud surface,for example by up to ±10° or more.

Novel aspects of the turbine blade and associated airfoil surfacesdescribed herein are achieved by substantial conformance to specifiedgeometries. Substantial conformance generally includes or may include amanufacturing tolerance of about ±0.050 inches (±1.27 mm), in order toaccount for variations in molding, cutting, shaping, surface finishingand other manufacturing processes, and to accommodate variability incoating thicknesses. This tolerance is generally constant or notscalable, and applies to each of the specified blade surfaces,regardless of size.

Substantial conformance is based on sets of points representing athree-dimensional surface with particular physical dimensions, forexample in inches or millimeters, as determined by selecting particularvalues of the scaling parameters. A substantially conforming airfoil,blade or vane structure has surfaces that conform to the specified setsof points, within the specified tolerance.

Alternatively, substantial conformance is based on a determination by anational or international regulatory body, for example in a partcertification or part manufacture approval (PMA) process for the FederalAviation Administration, the European Aviation Safety Agency, the CivilAviation Administration of China, the Japan Civil Aviation Bureau, orthe Russian Federal Agency for Air Transport. In these configurations,substantial conformance encompasses a determination that a particularpart or structure is identical to, or sufficiently similar to, thespecified airfoil, blade or vane, or that the part or structure issufficiently the same with respect to a part design in a type-certifiedor type-certificated airfoil, blade or vane, such that the part orstructure complies with airworthiness standards applicable to thespecified blade, vane or airfoil. In particular, substantial conformanceencompasses any regulatory determination that a particular part orstructure is sufficiently similar to, identical to, or the same as aspecified blade, vane or airfoil, such that certification orauthorization for use is based at least in part on the determination ofsimilarity.

Although an example embodiment has been disclosed, a worker of ordinaryskill in this art would recognize that certain modifications would comewithin the scope of the claims. For that reason, the following claimsshould be studied to determine their true scope and content.

What is claimed is:
 1. A turbine blade for a gas turbine enginecomprising: an airfoil including leading and trailing edges joined byspaced apart pressure and suction sides to provide an exterior airfoilsurface extending from a platform in a radial direction to a tip; andwherein the external airfoil surface is formed in substantialconformance with multiple cross-sectional profiles of the airfoildescribed by a set of Cartesian coordinates set forth in Table 1, theCartesian coordinates provided by an axial coordinate scaled by a localaxial chord, a circumferential coordinate scaled by a local axial chord,and a span location, wherein the local axial chord corresponds to awidth of the airfoil between the leading and trailing edges at the spanlocation.
 2. The turbine blade according to claim 1, wherein the airfoilis a first stage turbine blade.
 3. The turbine blade according to claim1, wherein the span location corresponds to a percentage of an overallspan distance in the radial direction from a point where the airfoilmeets the platform toward the tip.
 4. The turbine blade according toclaim 1, wherein the Cartesian coordinates in Table 1 have a tolerancerelative to the specified coordinates of ±0.050 inches (±1.27 mm).
 5. Agas turbine engine comprising: a compressor section; a combustor fluidlyconnected to the compressor section; a turbine section fluidly connectedto the combustor, the turbine section comprising: a high pressureturbine coupled to the high pressure compressor via a shaft; a lowpressure turbine; and wherein the high pressure turbine includes anarray of turbine blades, wherein at least one turbine blade includes anairfoil having leading and trailing edges joined by spaced apartpressure and suction sides to provide an exterior airfoil surfaceextending from a platform in a radial direction to a tip; and whereinthe external airfoil surface is formed in substantial conformance withmultiple cross-sectional profiles of the airfoil described by a set ofCartesian coordinates set forth in Table 1, the Cartesian coordinatesprovided by an axial coordinate scaled by a local axial chord, acircumferential coordinate scaled by a local axial chord, and a spanlocation, wherein the local axial chord corresponds to a width of theairfoil between the leading and trailing edges at the span location. 6.The gas turbine engine according to claim 5, wherein the array is afirst stage array of turbine blades.
 7. The gas turbine engine accordingto claim 6, wherein the high pressure turbine includes an array of fixedstator vanes upstream from the first stage array of turbine blades. 8.The gas turbine engine according to claim 6, wherein the first stagearray of turbine blades includes forty-four turbine blades.
 9. The gasturbine engine according to claim 5, wherein the span locationcorresponds to a percentage of an overall span distance in the radialdirection from a point where the airfoil meets the platform toward thetip.
 10. The gas turbine engine according to claim 5, wherein theCartesian coordinates in Table 1 have a tolerance relative to thespecified coordinates of ±0.050 inches (±1.27 mm).
 11. The gas turbineengine according to claim 5, wherein the high pressure turbine consistsof two arrays of turbine blades and two arrays of fixed stator vanes.